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AH 88-K-136/16 (ah88k136-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: AH 88-K-136/16 (ah88k136-il)
Reynolds number: 500,000
Max Cl/Cd: 113.25 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ah88k136-il-500000.txt
Download as CSV file: xf-ah88k136-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AH 88-K-136/16                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2158   0.10132   0.09865  -0.0690   0.8059   0.0255
 -11.500  -0.2206   0.09620   0.09354  -0.0719   0.8052   0.0258
 -11.250  -0.2224   0.09158   0.08894  -0.0740   0.8045   0.0259
 -11.000  -0.2259   0.08663   0.08400  -0.0762   0.8036   0.0260
 -10.750  -0.2351   0.08087   0.07827  -0.0772   0.8027   0.0266
 -10.500  -0.2349   0.07737   0.07478  -0.0781   0.8017   0.0269
 -10.250  -0.2351   0.07387   0.07129  -0.0791   0.8009   0.0272
 -10.000  -0.4508   0.04938   0.04630  -0.0952   0.8018   0.0165
  -9.750  -0.4634   0.04772   0.04456  -0.0911   0.8002   0.0167
  -9.500  -0.4887   0.04501   0.04166  -0.0847   0.7989   0.0167
  -9.250  -0.5224   0.03942   0.03561  -0.0771   0.7978   0.0158
  -9.000  -0.5340   0.03640   0.03220  -0.0718   0.7968   0.0159
  -8.750  -0.5400   0.03302   0.02847  -0.0674   0.7943   0.0158
  -8.500  -0.5387   0.03034   0.02537  -0.0635   0.7921   0.0159
  -8.250  -0.5337   0.02773   0.02232  -0.0600   0.7905   0.0163
  -8.000  -0.5214   0.02554   0.01988  -0.0578   0.7892   0.0168
  -7.750  -0.5025   0.02487   0.01914  -0.0566   0.7881   0.0175
  -7.500  -0.4829   0.02405   0.01818  -0.0553   0.7871   0.0182
  -7.250  -0.4623   0.02311   0.01706  -0.0541   0.7862   0.0189
  -7.000  -0.4405   0.02240   0.01617  -0.0530   0.7854   0.0199
  -6.750  -0.4183   0.02150   0.01507  -0.0520   0.7847   0.0208
  -6.500  -0.3964   0.02067   0.01422  -0.0513   0.7834   0.0222
  -6.250  -0.3729   0.02039   0.01393  -0.0510   0.7808   0.0237
  -6.000  -0.3490   0.01993   0.01340  -0.0505   0.7789   0.0250
  -5.750  -0.3253   0.01934   0.01271  -0.0499   0.7772   0.0263
  -5.500  -0.3031   0.01866   0.01203  -0.0491   0.7757   0.0285
  -5.250  -0.2794   0.01839   0.01172  -0.0484   0.7745   0.0308
  -5.000  -0.2554   0.01814   0.01140  -0.0477   0.7735   0.0326
  -4.750  -0.2347   0.01743   0.01068  -0.0464   0.7726   0.0359
  -4.500  -0.2107   0.01721   0.01043  -0.0457   0.7718   0.0395
  -4.250  -0.1887   0.01681   0.00999  -0.0446   0.7711   0.0440
  -3.750  -0.1450   0.01658   0.00981  -0.0431   0.7651   0.0552
  -3.500  -0.1213   0.01644   0.00966  -0.0425   0.7631   0.0627
  -3.250  -0.0987   0.01615   0.00941  -0.0415   0.7615   0.0731
  -3.000  -0.0751   0.01589   0.00919  -0.0408   0.7603   0.0866
  -2.750  -0.0512   0.01562   0.00896  -0.0400   0.7592   0.1058
  -2.500  -0.0279   0.01529   0.00874  -0.0392   0.7584   0.1386
  -2.250  -0.0060   0.01486   0.00852  -0.0381   0.7575   0.1956
  -2.000   0.0079   0.01439   0.00855  -0.0359   0.7544   0.3256
  -1.750   0.0064   0.01353   0.00858  -0.0307   0.7495   0.5586
  -1.500   0.0509   0.01289   0.00913  -0.0334   0.7486   0.8807
  -1.250   0.0732   0.01316   0.00935  -0.0316   0.7471   0.9043
  -1.000   0.1120   0.01346   0.00958  -0.0334   0.7462   0.9172
  -0.750   0.1576   0.01381   0.00986  -0.0365   0.7456   0.9290
  -0.500   0.2491   0.01431   0.01028  -0.0494   0.7457   0.9334
  -0.250   0.2862   0.01446   0.01038  -0.0509   0.7448   0.9436
   0.000   0.3606   0.01450   0.01035  -0.0604   0.7446   0.9473
   0.250   0.4113   0.01450   0.01030  -0.0649   0.7441   0.9552
   0.500   0.4459   0.01425   0.01001  -0.0663   0.7434   0.9594
   0.750   0.4843   0.01392   0.00964  -0.0686   0.7428   0.9610
   1.000   0.5165   0.01412   0.00990  -0.0703   0.7367   0.9637
   1.250   0.5486   0.01391   0.00969  -0.0714   0.7346   0.9668
   1.500   0.5719   0.01376   0.00951  -0.0704   0.7330   0.9716
   1.750   0.6101   0.01327   0.00902  -0.0727   0.7318   0.9728
   2.000   0.6469   0.01284   0.00858  -0.0747   0.7307   0.9743
   2.250   0.6823   0.01241   0.00813  -0.0764   0.7296   0.9761
   2.500   0.7162   0.01202   0.00773  -0.0778   0.7284   0.9781
   2.750   0.7416   0.01213   0.00793  -0.0778   0.7222   0.9814
   3.000   0.7711   0.01185   0.00767  -0.0782   0.7192   0.9840
   3.250   0.8072   0.01135   0.00718  -0.0801   0.7168   0.9853
   3.500   0.8428   0.01085   0.00667  -0.0818   0.7144   0.9867
   3.750   0.8729   0.01075   0.00666  -0.0827   0.7078   0.9887
   4.000   0.9044   0.01041   0.00634  -0.0836   0.7028   0.9906
   4.250   0.9349   0.01015   0.00611  -0.0843   0.6984   0.9924
   4.500   0.9631   0.01004   0.00608  -0.0847   0.6894   0.9943
   4.750   0.9955   0.00973   0.00582  -0.0859   0.6783   0.9957
   5.000   1.0261   0.00937   0.00540  -0.0866   0.6552   0.9973
   5.250   1.0521   0.00929   0.00519  -0.0864   0.6155   0.9989
   5.500   1.0707   0.00961   0.00522  -0.0848   0.5578   1.0000
   5.750   1.0789   0.01033   0.00564  -0.0813   0.5006   1.0000
   6.000   1.0887   0.01104   0.00614  -0.0784   0.4548   1.0000
   6.500   1.1024   0.01274   0.00739  -0.0718   0.3591   1.0000
   6.750   1.1050   0.01372   0.00813  -0.0680   0.3113   1.0000
   7.000   1.1046   0.01471   0.00891  -0.0636   0.2690   1.0000
   7.250   1.0964   0.01578   0.00979  -0.0580   0.2269   1.0000
   7.500   1.0744   0.01670   0.01059  -0.0497   0.2019   1.0000
   7.750   1.0564   0.01776   0.01151  -0.0426   0.1731   1.0000
   8.000   1.0393   0.01902   0.01251  -0.0359   0.1299   1.0000
   8.250   1.0241   0.02038   0.01357  -0.0297   0.0822   1.0000
   8.500   1.0098   0.02184   0.01474  -0.0238   0.0421   1.0000
   8.750   1.0106   0.02270   0.01558  -0.0200   0.0333   1.0000
   9.000   1.0090   0.02372   0.01658  -0.0160   0.0277   1.0000
   9.250   1.0149   0.02438   0.01730  -0.0131   0.0255   1.0000
   9.500   1.0181   0.02520   0.01815  -0.0098   0.0235   1.0000
   9.750   1.0157   0.02634   0.01933  -0.0060   0.0217   1.0000
  10.000   1.0196   0.02714   0.02021  -0.0030   0.0209   1.0000
  10.250   1.0232   0.02799   0.02111   0.0001   0.0197   1.0000
  10.500   1.0267   0.02885   0.02201   0.0030   0.0186   1.0000
  10.750   1.0281   0.02990   0.02308   0.0061   0.0178   1.0000
  11.000   1.0246   0.03135   0.02458   0.0094   0.0170   1.0000
  11.250   1.0258   0.03269   0.02599   0.0121   0.0162   1.0000
  11.500   1.0312   0.03392   0.02729   0.0142   0.0159   1.0000
  11.750   1.0374   0.03519   0.02864   0.0160   0.0154   1.0000
  12.000   1.0428   0.03662   0.03013   0.0177   0.0149   1.0000
  12.250   1.0495   0.03801   0.03157   0.0192   0.0143   1.0000
  12.500   1.0557   0.03950   0.03310   0.0207   0.0138   1.0000
  12.750   1.0607   0.04113   0.03475   0.0221   0.0132   1.0000
  13.000   1.0645   0.04292   0.03661   0.0238   0.0125   1.0000
  13.250   1.0738   0.04430   0.03809   0.0247   0.0122   1.0000
  13.500   1.0821   0.04582   0.03970   0.0260   0.0120   1.0000
  13.750   1.0903   0.04736   0.04134   0.0269   0.0115   1.0000
  14.000   1.0980   0.04900   0.04307   0.0279   0.0111   1.0000
  14.250   1.1056   0.05070   0.04485   0.0290   0.0108   1.0000
  14.500   1.1136   0.05239   0.04665   0.0298   0.0108   1.0000
  14.750   1.1180   0.05439   0.04870   0.0303   0.0103   1.0000
  15.000   1.1239   0.05637   0.05076   0.0312   0.0101   1.0000
  15.250   1.1296   0.05842   0.05288   0.0321   0.0098   1.0000
  15.500   1.1331   0.06080   0.05544   0.0328   0.0100   1.0000
  16.250   1.1193   0.07152   0.06675   0.0349   0.0095   1.0000
  16.500   1.1097   0.07575   0.07118   0.0348   0.0095   1.0000
  16.750   1.0962   0.08044   0.07609   0.0336   0.0093   1.0000
  17.000   1.0856   0.08532   0.08112   0.0337   0.0095   1.0000
  17.500   1.0555   0.09641   0.09259   0.0298   0.0094   1.0000
  17.750   0.8365   0.15098   0.14862   0.0049   0.0199   1.0000
  18.000   0.5854   0.15228   0.15012   0.0084   0.0238   1.0000
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